EP3660280A1 - Vorrichtung, anordnungen und verfahren zur verringerung des thermischen bogens im rotor eines motors beim anlassen - Google Patents

Vorrichtung, anordnungen und verfahren zur verringerung des thermischen bogens im rotor eines motors beim anlassen Download PDF

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Publication number
EP3660280A1
EP3660280A1 EP19204060.8A EP19204060A EP3660280A1 EP 3660280 A1 EP3660280 A1 EP 3660280A1 EP 19204060 A EP19204060 A EP 19204060A EP 3660280 A1 EP3660280 A1 EP 3660280A1
Authority
EP
European Patent Office
Prior art keywords
rotor
engine
module
acceleration
threshold speed
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP19204060.8A
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English (en)
French (fr)
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EP3660280B1 (de
Inventor
Kevin Brown
Christopher Hodges
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Boeing Co
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Boeing Co
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Publication of EP3660280A1 publication Critical patent/EP3660280A1/de
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • F01D19/02—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith dependent on temperature of component parts, e.g. of turbine-casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/10—Heating, e.g. warming-up before starting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/34—Turning or inching gear
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/85—Starting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/304—Spool rotational speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/334—Vibration measurements
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This disclosure relates generally to start-up techniques for an engine, and more particularly to mitigating thermal bow in the rotor of an engine at start-up.
  • the subject matter of the present application has been developed in response to the present state of the art, and in particular, in response to the shortcomings of conventional start-up techniques that attempt to mitigate thermal bow in the rotor of an engine at start-up, that have not yet been fully solved by currently available techniques. Accordingly, the subject matter of the present application has been developed to provide a start-up apparatus, a start-up assembly, and associated method that overcome at least some of the above-discussed shortcomings of prior art techniques.
  • One apparatus includes a control module that facilitates operating the rotor prior to initiating fuel flow and ignition of the engine and an acceleration module that facilitates accelerating the rotor to at least a threshold speed within a predetermined amount of time prior to initiating fuel flow and ignition of the engine. Further, at least a portion of the control module and/or the acceleration module includes one or more of a set of hardware circuits, a set of programmable hardware devices, and executable code stored on a set of non-transitory computer-readable storage mediums.
  • the acceleration module is configured to facilitate accelerating the rotor to the threshold speed at a constant rate of acceleration with a selected rate of acceleration and with an amount of engine rub that is less than an unacceptable amount of engine rub.
  • the acceleration module is configured to facilitate accelerating the rotor to the threshold speed at a maximum rate of acceleration to reach the threshold speed in a minimum amount of time while avoiding excessive rub.
  • the apparatus further includes a speed module that determines the threshold speed based on a relationship of time and a set of conditions for the rotor detected at the start-up of the engine.
  • the apparatus also includes an input module that receives, from a set of sensors, a set of sensor inputs corresponding to the set of conditions for the rotor detected at a start-up of the engine or an elapsed time since a previous shutdown of the engine.
  • the speed module is configured to determine the threshold speed based on one or more sensor inputs of the set of sensor inputs corresponding to the set of conditions for the rotor detected at the start-up of the engine.
  • the set of sensor inputs includes one or more of a temperature of the rotor, a speed of the rotor, an amount of vibration of the rotor, and an amount of rotor excursion at the start-up of the engine.
  • the apparatus includes a condition module that maintains a preset set of acceleration inputs corresponding to a set of predetermined conditions for the rotor at the start-up of the engine.
  • the preset set of acceleration inputs comprises one or more of a preset temperature, a preset speed of the rotor, a preset amount of vibration of the rotor, and a preset amount of rotor excursion and the acceleration module is configured to facilitate accelerating the rotor to the threshold speed based on the preset set of acceleration inputs.
  • start-up assemblies for mitigating thermal bow in the rotor of an aircraft engine at start-up.
  • One assembly includes a start-up device coupleable to the rotor and configured to accelerate the rotor and a start-up module coupled to the start-up device.
  • the start-up device and the start-up module are configured to coordinate operations to accelerate the rotor to at least a threshold speed within a predetermined amount of time prior to initiating fuel flow and ignition of the aircraft engine.
  • the start-up module includes a control module for controlling the rotor at start-up of the engine and an acceleration module for accelerating the rotor to the threshold speed within the predetermined amount of time.
  • the start-up module is configured to accelerate the rotor to the threshold speed at a constant rate of acceleration or a maximum rate of acceleration to reach the threshold speed in a minimum amount of time while avoiding excessive engine rub.
  • the start-up module includes a speed module that determines the threshold speed based on a relationship of time and a set of conditions for the rotor detected at start-up of the aircraft engine.
  • the assembly includes a set of sensors coupled to the rotor.
  • the start-up module further includes an input module that receives, from the set of sensors, a set of sensor inputs corresponding to the set of conditions for the rotor detected at the start-up of the engine and the speed module is configured to determine the threshold speed based on one or more sensor inputs of the set of sensor inputs corresponding to the set of conditions for the rotor detected at the start-up of the engine.
  • the set of sensors includes one or more of a temperature sensor for detecting a temperature of the rotor, a velocity sensor for detecting a speed of the rotor, a vibration sensor for detecting an amount of vibration of the rotor, and an excursion sensor for detecting an amount of rotor excursion at the start-up of the engine.
  • the start-up module is further configured to maintain a preset set of acceleration inputs corresponding to a set of predetermined conditions for the rotor at the start-up of the aircraft engine.
  • the preset set of acceleration inputs includes one or more of a preset temperature, a preset speed of the rotor, a preset amount of vibration of the rotor, and a preset amount of rotor excursion and the start-up module is configured to accelerate the rotor to the threshold speed based on the preset set of acceleration inputs.
  • One method includes transmitting, by a processor, a control signal to a start-up device to control the rotor prior to initiating fuel flow and ignition for the engine and accelerating, via the start-up device, the rotor to at least a threshold speed within a predetermined amount of time prior to initiating fuel flow and ignition of the engine.
  • Accelerating the rotor includes accelerating the rotor to the threshold speed at a constant rate of acceleration or accelerating the rotor to the threshold speed at a maximum rate of acceleration to reach the threshold speed in a minimum amount of time without incurring excessive engine rub.
  • the method further includes determining the threshold speed based on a relationship of time and a set of conditions for the rotor detected at the start-up of the engine.
  • the method further includes receiving, from a set of sensors, a set of sensor inputs corresponding to the set of conditions for the rotor detected at the start-up of the engine.
  • the threshold speed is determined based on one or more sensor inputs of the set of sensor inputs corresponding to the set of conditions for the rotor detected at the start-up of the engine.
  • the set of sensor inputs includes one or more of a temperature of the rotor, a speed of the rotor, an amount of vibration of the rotor, and an amount of rotor excursion at the start-up of the engine.
  • the method further includes maintaining a preset set of acceleration inputs corresponding to a set of predetermined conditions for the rotor at the start-up of the engine.
  • the preset set of acceleration inputs comprises one or more of a preset temperature, a preset speed of the rotor, a preset amount of vibration of the rotor, and a preset amount of rotor excursion and accelerating the rotor further comprises accelerating the rotor to the threshold speed based on the preset set of predetermined acceleration inputs.
  • an aircraft engine 50 that includes a rotor 75 (see Figure 7 ) is coupled to one embodiment of a start-up assembly 100 (and/or system) for mitigating thermal bow in the rotor 75 at start-up of the aircraft engine 50.
  • the start-up assembly 100 includes, among other components, a set of sensors 202, a start-up device 204, and a processor 206.
  • the set of sensors 202 (also simply referred individually, in various groups, or collectively as sensor(s) 202) is coupled to and/or are in communication with one or more positions/locations in, on, and/or proximate to the aircraft engine 50. That is, the sensor(s) 202 may be located in one or more positions that allow the sensor(s) 202 to detect/sense one or more conditions and/or physical states for the aircraft engine 50.
  • the set of sensors 202 includes one type of sensor 202. In additional or alternative embodiments, the set of sensors 202 includes two or more different types of sensors 202. Further, each type of sensor 202 can include one or more sensors 202 for each different sensor type. In some embodiments, at least two different sensor types include different quantities of sensors 202 such that each of the at least two sensor types include a set or subset of sensors 202.
  • the set of sensors 202 is configured to transmit one or more signals to a processor 206 in response to detecting/sensing the condition(s) and/or physical state of the aircraft engine 50.
  • the signal(s) provide a set of sensor inputs that are used as the basis for determining the speed at which the rotor 75 should operate/rotate prior to starting the aircraft engine 50 in an effort to mitigate the effects of thermal bow in the rotor 75.
  • the set of sensor inputs are used to calculate a threshold speed (e.g., a minimal speed) for the rotor 75.
  • the threshold speed corresponds with a speed that helps to eliminate thermal bow in the rotor 75 or reduce the amount of thermal bow (e.g., reduce to an acceptable amount) in the rotor 75 at the start-up (e.g., prior to initiating fuel flow and ignition) of the aircraft engine 50.
  • the aircraft engine 50 is able to start-up with no rub or a minimal/acceptable amount of rub between moving and static parts in the aircraft engine 50. Further, reducing thermal bow allows the aircraft engine 50 to operate more efficiently because the gap between moving and static parts in the aircraft engine 50 is reduced and/or optimized.
  • the set of sensors 202 includes one or more temperature sensors 302.
  • Each temperature sensor 302 is configured to sense and/or detect the temperature and/or thermal condition of one or more locations of the aircraft engine 50 that are on, in, or proximate to the rotor 75.
  • multiple temperature sensors 302 are located at different positions on, in, or proximate to the rotor 75 to detect, sense, and/or determine a temperature gradient within the aircraft engine 50 corresponding to the rotor 75.
  • the temperature sensor(s) 302 are configured to transmit a signal (e.g., a temperature input) to the processor 206 in response to detecting the temperature and/or thermal condition of one or more locations of the aircraft engine 50 that are on, in, or proximate to the rotor 75.
  • the temperature input(s) are used as at least a partial basis for determining the speed at which the rotor 75 should operate/rotate prior to starting the aircraft engine 50 in an effort to mitigate the effects of thermal bow in the rotor 75.
  • the temperature sensor input(s) are used to calculate a threshold speed (e.g., a minimal speed) for the rotor 75, which calculation is used to determine a speed for the rotor 75 prior to starting the aircraft engine 50 in an effort to eliminate thermal bow in the rotor 75 or reduce the amount of thermal bow (e.g., reduce to an acceptable amount) in the rotor 75 at the start-up of the aircraft engine 50.
  • a threshold speed e.g., a minimal speed
  • the set of sensors 202 includes one or more velocity sensors 304.
  • Each velocity sensor 304 is configured to sense and/or detect the speed and/or velocity of one or more locations and/or portions of the rotor 75.
  • multiple velocity sensors 304 are located at different positions on, in, or proximate to the rotor 75 to detect, sense, and/or determine the speed/velocity of the rotor 75.
  • the velocity sensor(s) 304 are configured to transmit a signal (e.g., a velocity input and/or speed input) to the processor 206 in response to detecting the speed and/or velocity of one or more locations and/or portions of the rotor 75.
  • the velocity input(s) are used as at least a partial basis for determining the speed at which the rotor 75 should operate/rotate prior to starting the aircraft engine 50 in an effort to mitigate the effects of thermal bow in the rotor 75.
  • the velocity sensor input(s) are used to calculate a threshold speed (e.g., a minimal speed) for the rotor 75, which calculation is used to determine a speed for the rotor 75 prior to starting the aircraft engine 50 in an effort to eliminate thermal bow in the rotor 75 or reduce the amount of thermal bow (e.g., reduce to an acceptable amount) in the rotor 75 at the start-up of the aircraft engine 50.
  • a threshold speed e.g., a minimal speed
  • the set of sensors 202 includes one or more vibration sensors 306.
  • Each vibration sensor 306 is configured to sense and/or detect the amount of vibration in one or more locations and/or portions of the rotor 75. In some embodiments, multiple vibration sensors 306 are located at different positions on, in, or proximate to the rotor 75 to detect, sense, and/or determine the amount of vibration in the rotor 75.
  • the vibration sensor(s) 306 are configured to transmit a signal (e.g., a vibration input) to the processor 206 in response to detecting the amount of vibration in one or more locations and/or portions of the rotor 75.
  • the vibration input(s) are used as at least a partial basis for determining the speed at which the rotor 75 should operate/rotate prior to starting the aircraft engine 50 in an effort to mitigate the effects of thermal bow in the rotor 75.
  • the vibration sensor input(s) are used to calculate a threshold speed (e.g., a minimal speed) for the rotor 75, which calculation is used to determine a speed for the rotor 75 prior to starting the aircraft engine 50 in an effort to eliminate thermal bow in the rotor 75 or reduce the amount of thermal bow (e.g., reduce to an acceptable amount) in the rotor 75 at the start-up of the aircraft engine 50.
  • a threshold speed e.g., a minimal speed
  • the set of sensors 202 includes one or more excursion sensors 306.
  • Each excursion sensor 306 is configured to sense and/or detect the amount of excursion (e.g., the amount of off-axis bow) in one or more locations and/or portions of the rotor 75.
  • multiple excursion sensors 308 are located at different positions on, in, or proximate to the rotor 75 to detect, sense, and/or determine the amount of excursion in the rotor 75.
  • the excursion sensor(s) 308 are configured to transmit a signal (e.g., an excursion input) to the processor 206 in response to detecting the amount of excursion in one or more locations and/or portions of the rotor 75.
  • the excursion input(s) are used as at least a partial basis for determining the speed at which the rotor 75 should operate/rotate prior to starting the aircraft engine 50 in an effort to mitigate the effects of thermal bow in the rotor 75.
  • the excursion sensor input(s) are used to calculate a threshold speed (e.g., a minimal speed) for the rotor 75, which calculation is used to determine a speed for the rotor 75 prior to starting the aircraft engine 50 in an effort to eliminate thermal bow in the rotor 75 or reduce the amount of thermal bow (e.g., reduce to an acceptable amount) in the rotor 75 at the start-up of the aircraft engine 50.
  • a threshold speed e.g., a minimal speed
  • the start-up assembly 100 further includes a start-up device 204.
  • the start-up device 204 may include any suitable apparatus, system, and/or assembly that can operate and/or rotate the rotor 75 at a predetermined and/or threshold speed while the aircraft engine 50 is OFF and/or prior to starting the aircraft engine 50.
  • the start-up device 204 is configured to accelerate the rotor 75 to the predetermined and/or threshold speed at constant rate of acceleration.
  • the start-up device 204 is configured to accelerate the rotor 75 to the predetermined and/or threshold speed at a maximum rate of acceleration. That is, the start-up device 204 can be configured to accelerate the rotor 75 to the predetermined and/or threshold speed as quickly as possible or in a minimal amount of time.
  • the amount of time taken by the initial acceleration may be considered insignificant compared to the overall mitigation time prior to engine start.
  • the start-up device 204 is configured to accelerate the rotor 75 to the predetermined and/or threshold speed at an intermediate rate of acceleration. That is, the rotor can be accelerated to the predetermined and/or threshold speed at a rate of acceleration that is between the constant rate of acceleration and the maximum rate of acceleration.
  • a start-up device 204A, 204C includes a gear box 402 of the aircraft engine 50.
  • the gear box 402 may include any suitable hardware and/or gearing mechanism that is known or developed in the future that is capable of accelerating the rotor 75 to the predetermined/threshold speed and operating/rotating the rotor 75 at the predetermined/threshold speed the while the aircraft engine 50 is OFF and/or prior to starting the aircraft engine 50.
  • a start-up device 204B, 204C includes a start-up motor 406 of the aircraft engine 50.
  • the start-up motor 406 may include any suitable hardware and/or motor that is known or developed in the future that is capable of accelerating the rotor 75 to the predetermined/threshold speed and operating/rotating the rotor 75 at the predetermined/threshold speed the while the aircraft engine 50 is OFF and/or prior to starting the aircraft engine 50.
  • the start-up assembly 100 further includes a processor 206.
  • a processor 206 may include any suitable processing hardware and/or software capable of performing computer processes, functions, and/or algorithms.
  • a processor 206 is configured to facilitate operating the rotor 75 prior to starting the aircraft engine 50.
  • the processor 206 includes a start-up module 502 that facilitates operating the rotor 75 prior to starting the aircraft engine 50 via the start-up device 204 (e.g., start-up device 204A, start-up device 204B, and start-up device 204C (also simply referred individually, in various groups, or collectively as start-up device(s) 204)).
  • the start-up module 502 may include any suitable hardware and/or software that can control and/or manage a start-up device 204 to facilitate accelerating the rotor 75 to a predetermined/threshold speed within a minimal amount of time prior to starting the aircraft engine 50.
  • Reducing or eliminating thermal bow in the rotor 75 eliminates or at least reduces the quantity of moving parts and/or the amount that moving parts rub with other static parts upon starting of the aircraft engine 50. Further, reducing or eliminating thermal bow in the rotor 75 decreases the gaps between moving and static parts of the aircraft engine 50, which increases the efficiency of operations for the aircraft engine 50.
  • FIGS 6A through 6D are block diagrams of various embodiments of a start-up module 502 (e.g., start-up module 502A, start-up module 502B, start-up module 502C, and start-up module 502D (also simply referred individually, in various groups, or collectively as start-up module(s) 502)).
  • the start-up module 502A includes, among other components, a control module 602 and an acceleration module 604.
  • the start-up module 502B includes, among other components, the control module 602, the acceleration module 604, a speed module 606, and an input module 608.
  • the start-up module 502C includes, among other components, the control module 602, the acceleration module 604, and a condition module 610.
  • the start-up module 502D includes, among other components, the control module 602, the acceleration module 604, the speed module 606, the input module 608, and the condition module 610.
  • a control module 602 includes suitable hardware and/or software that can control and/or manage one or more operations of a start-up device 204.
  • the control module 602 commands the start-up device 204 to operate the rotor 75 at a predetermined/threshold speed prior to start-up of the aircraft engine 50.
  • the predetermined/threshold speed is based on a calculated speed received from the speed module 606.
  • An acceleration module 604 includes suitable hardware and/or software that can control and/or manage one or more operations of a start-up device 204.
  • the acceleration module 604 commands the start-up device 204 to accelerate the rotor 75 to the predetermined/threshold speed within a predetermined amount of time prior to start-up of the aircraft engine 50.
  • the acceleration module 604 commands the start-up device 204 to accelerate the rotor 75 to the predetermined/threshold speed at a constant or substantially constant rate of acceleration. In additional or alternative embodiments, the acceleration module 604 commands the start-up device 204 to accelerate the rotor 75 to the predetermined/threshold speed at a maximum rate of acceleration. That is, the acceleration module 604 commands the start-up device 204 to accelerate the rotor 75 to the predetermined/threshold speed as quickly as possible or in a minimal amount of time.
  • the predetermined amount of time is equal to the least amount of time as possible.
  • a speed module 606 includes suitable hardware and/or software that can calculate and/or determine the predetermined/threshold speed and/or the amount of time to accelerate the rotor 75 until the thermal bow becomes zero or substantially zero (e.g., less than or equal to an acceptable amount of thermal bow).
  • the predetermined/threshold speed in various embodiments, is based on one or more conditions detected/sensed in, on, and/or proximate to the rotor 75 of the aircraft engine 50.
  • B represents thermal bow in the rotor 75 in terms of excursion (e.g., off-axis thermal bow) outside ideal rotor envelope swept out in quasi-static rotation
  • E represents excursion outside ideal rotor envelope due to bow and vibration
  • N represents high pressure (HP) rotor speed (e.g., revolutions-per-minute (RPM)).
  • HP revolutions-per-minute
  • the relation E B(1 + kN) is based on the effect of vibration increasing linearly with B and linearly with the rotational speed N.
  • the real amount of vibration may increase as the square of the rotational speed (e.g., because the acceleration of a particle moving at speed v in a circle of radius r is v 2 /r). In some embodiments, vibration is deemed linear.
  • the rotor 75 is accelerated at the constant rate until the thermal bow in the rotor 75 is zero or substantially zero (e.g., less than or equal to an acceptable amount of thermal bow).
  • the maximum excursion is independent of u.
  • the rotor 75 is rapidly accelerated while the thermal bow in the rotor 75 is at or below a maximum allowable amount of excursion.
  • this technique presumes that the initial bow does not exceed 5 mils (equivalent to about 0,127 mm) and that the maximum allowable excursion is 7.58 mils (equivalent to about 0,1925 mm).
  • the rotor 75 is initially accelerated to 250 RPMs as quickly as possible and then follow an optimum acceleration schedule of constant E up to N f .
  • a three-part process is utilized to determine the time required to eliminate the thermal bow with the maximum acceleration technique.
  • This acceleration can take place as rapidly as possible, and can be considered instantaneous or substantially instantaneous (e.g., 0 seconds).
  • E m B 1 + kN .
  • ⁇ t phase 2 kE m u 1 1 + kN f ⁇ 1 1 + kN i + ln 1 + kN i N f 1 + kN f N i .
  • Figure 16 shows the acceleration profile for one example of the maximum rate of acceleration technique.
  • N i 258 RPMs
  • the second phase takes 52.4 seconds, so the entire process takes 77.6 seconds, compared with 100 seconds for the constant rate acceleration technique.
  • a reduction of 22.4 seconds assumes that the first phase of acceleration occurs instantly, whereas it would actually require some amount of time, depending on the maximum acceleration capability of the start-up device 204.
  • the start time of 77.6 seconds can be decreased further if the rotor 75 can be operated at a higher speed than 1000 RPMs.
  • Figure 17 shows the total start time for the above example as a function of N f .
  • Figure 17 shows that if the rotor 75 can be accelerated up to 2000 RPMs, the start time decreases to 67.4 seconds and if accelerated up to 3000 RPMs, the start time decreases to 65.3 seconds.
  • the rate of acceleration at the end of the constant-E phase goes to infinity as N f increases, so the limit is imposed by the maximum achievable acceleration of the rotor 75 by the start-up device 204.
  • the input module 608 is configured to receive one or more inputs (e.g., sensor signals) from the set of sensors 202.
  • the one or more inputs correspond to one or more conditions detected/sensed in, on, and/or proximate to the rotor 75 of the aircraft engine 50.
  • the input module 608 can receive one or more of a temperature input of the rotor 75 (e.g., a temperature input signal) from the temperature sensor 302, a velocity input of the rotor 75 (e.g., a velocity input signal) from the velocity sensor 304, a vibration input of the rotor 75 (e.g., a vibration input signal) from the vibration sensor 306, and an excursion input of the rotor 75 (e.g., an excursion input signal) from the excursion sensor 308.
  • the system can also sense when the engine was previously shut down (e.g., based on the fuel control switch position), and at the next start-up the system can determine the time elapsed since the previous shutdown, which can be used to estimate the amount of initial bow.
  • the use of at least the set of sensors 202, the speed module 606, and the input module 608 can constitute an open loop system.
  • Some embodiments include a condition module 610 that maintains a preset set of acceleration inputs corresponding to one or more predetermined/preset conditions for the rotor 75.
  • the preset set of acceleration inputs can include one or more of a preset temperature input of the rotor 75 (e.g., a temperature input signal), a velocity input of the rotor 75 (e.g., a velocity input signal), a vibration input of the rotor 75 (e.g., a vibration input signal), and an excursion input of the rotor 75 (e.g., an excursion input signal), and the time elapsed since the previous shutdown.
  • the use and maintenance of the preset set of acceleration inputs can constitute a closed loop system.
  • Figures 8 through 11 are flow diagrams illustrating various embodiments of a method 800, 900, 1000, 1100 for mitigating thermal bow in a rotor 75 of an aircraft engine 50.
  • the various methods 800, 900, 1000, 1100 By eliminating or reducing thermal bow, the aircraft engine 50 is able to start-up with no rub or a minimal/acceptable amount of rub between moving and static parts in the aircraft engine 50. Further, reducing thermal bow allows the aircraft engine 50 to operate more efficiently because the gap between moving and static parts in the aircraft engine 50 is reduced and/or optimized.
  • the method 800 begins by the processor 206 transmitting a control signal to a start-up device 204 to control the rotor 75 of an aircraft engine prior to starting the aircraft engine 50 (block 802).
  • the processor 206 commands the start-up device 204 to accelerate the rotor 75 to at least a predetermined and/or threshold speed within a predetermined amount of time prior to starting the aircraft engine (block 804).
  • the method 900 begins by a processor 206 determining a predetermined and/or threshold speed for the rotor 75 of an aircraft engine 50 (block 902).
  • the determination in some embodiments, is based on one or more sensor inputs corresponding to one or more detected/sensed conditions of the rotor 75.
  • the processor 206 transmits a control signal to a start-up device 204 to control the rotor 75 of an aircraft engine prior to starting the aircraft engine 50 (block 904).
  • the processor 206 commands the start-up device 204 to accelerate the rotor 75 to at least the predetermined and/or threshold speed within a predetermined amount of time prior to starting the aircraft engine (block 906).
  • the method 1000 begins by a processor 206 receiving a set of sensor inputs from a set of sensors 202 corresponding to one or more detected/sensed conditions of the rotor 75 of an aircraft engine 50 (block 1002).
  • the processor 206 determines a predetermined and/or threshold speed for the rotor 75 based on the set of sensor inputs (block 1004).
  • the processor 206 transmits a control signal to a start-up device 204 to control the rotor 75 of an aircraft engine prior to starting the aircraft engine 50 (block 1006).
  • the processor 206 commands the start-up device 204 to accelerate the rotor 75 to at least the predetermined and/or threshold speed within a predetermined amount of time prior to starting the aircraft engine (block 1008).
  • the method 1100 begins by a processor 206 maintaining a preset set of acceleration inputs corresponding to a set of predetermined conditions for the rotor 75 of an aircraft engine 50 (block 1102).
  • the preset set of conditions are the basis for a predetermined and/or threshold speed for the rotor 75 prior to starting the aircraft engine 50.
  • the processor 206 transmits a control signal to a start-up device 204 to control the rotor 75 of an aircraft engine prior to starting the aircraft engine 50 (block 1104).
  • the processor 206 commands the start-up device 204 to accelerate the rotor 75 to at least the predetermined and/or threshold speed within a predetermined amount of time prior to starting the aircraft engine (block 1106).
  • instances in this specification where one element is "coupled" to another element can include direct and indirect coupling.
  • Direct coupling can be defined as one element coupled to and in some contact with another element.
  • Indirect coupling can be defined as coupling between two elements not in direct contact with each other, but having one or more additional elements between the coupled elements.
  • securing one element to another element can include direct securing and indirect securing.
  • adjacent does not necessarily denote contact. For example, one element can be adjacent another element without being in contact with that element.
  • the phrase "at least one of', when used with a list of items, means different combinations of one or more of the listed items may be used and only one of the items in the list may be needed.
  • the item may be a particular object, thing, or category.
  • "at least one of' means any combination of items or number of items may be used from the list, but not all of the items in the list may be required.
  • "at least one of item A, item B, and item C" may mean item A; item A and item B; item B; item A, item B, and item C; or item B and item C.
  • "at least one of item A, item B, and item C” may mean, for example, without limitation, two of item A, one of item B, and ten of item C; four of item B and seven of item C; or some other suitable combination.
  • first, second, etc. are used herein merely as labels, and are not intended to impose ordinal, positional, or hierarchical requirements on the items to which these terms refer. Moreover, reference to, e.g., a “second” item does not require or preclude the existence of, e.g., a "first” or lower-numbered item, and/or, e.g., a "third" or higher-numbered item.
  • set can mean “one or more,” unless expressly specified otherwise.
  • sets can mean multiples of or a plurality of "one or mores,” “ones or more,” and/or “ones or mores” consistent with set theory, unless expressly specified otherwise.
  • a system, apparatus, structure, article, element, component, or hardware “configured to” perform a specified function is indeed capable of performing the specified function without any alteration, rather than merely having potential to perform the specified function after further modification.
  • the system, apparatus, structure, article, element, component, or hardware “configured to” perform a specified function is specifically selected, created, implemented, utilized, programmed, and/or designed for the purpose of performing the specified function.
  • "configured to” denotes existing characteristics of a system, apparatus, structure, article, element, component, or hardware which enable the system, apparatus, structure, article, element, component, or hardware to perform the specified function without further modification.
  • a system, apparatus, structure, article, element, component, or hardware described as being “configured to” perform a particular function may additionally or alternatively be described as being “adapted to” and/or as being “operative to” perform that function.
  • the present technology may be a system, a method, and/or a computer program product.
  • the computer program product may include a computer-readable storage medium (or media) including computer-readable program instructions thereon for causing a processor to carry out aspects of the present technology.
  • the computer-readable storage medium can be a tangible device that can retain and store instructions for use by an instruction execution device.
  • the computer-readable storage medium may be, for example, but is not limited to, an electronic storage device, a magnetic storage device, an optical storage device, an electromagnetic storage device, a semiconductor storage device, or any suitable combination of the foregoing.
  • a non-exhaustive list of more specific examples of the computer-readable storage medium includes the following: a portable computer diskette, a hard disk, a random access memory (“RAM”), a read-only memory (“ROM”), an erasable programmable read-only memory (“EPROM” or Flash memory), a static random access memory (“SRAM”), a portable compact disc read-only memory (“CD-ROM”), a digital versatile disk (“DVD”), a memory stick, a floppy disk, a mechanically encoded device such as punch-cards or raised structures in a groove including instructions recorded thereon, and any suitable combination of the foregoing.
  • RAM random access memory
  • ROM read-only memory
  • EPROM erasable programmable read-only memory
  • SRAM static random access memory
  • CD-ROM compact disc read-only memory
  • DVD digital versatile disk
  • memory stick a floppy disk
  • mechanically encoded device such as punch-cards or raised structures in a groove including instructions recorded thereon
  • a computer-readable storage medium is not to be construed as being transitory signals per se, such as radio waves or other freely propagating electromagnetic waves, electromagnetic waves propagating through a waveguide or other transmission media (e.g., light pulses passing through a fibre-optic cable), or electrical signals transmitted through a wire.
  • Computer-readable program instructions described herein can be downloaded to respective computing/processing devices from a computer-readable storage medium or to an external computer or external storage device via a network, for example, the Internet, a local area network, a wide area network and/or a wireless network.
  • the network may comprise copper transmission cables, optical transmission fibres, wireless transmission, routers, firewalls, switches, gateway computers and/or edge servers.
  • a network adapter card or network interface in each computing/processing device receives computer-readable program instructions from the network and forwards the computer-readable program instructions for storage in a computer-readable storage medium within the respective computing/processing device.
  • Computer-readable program instructions for carrying out operations of the present technology may be assembler instructions, instruction-set-architecture (ISA) instructions, machine instructions, machine dependent instructions, microcode, firmware instructions, state-setting data, or either source code or object code written in any combination of one or more programming languages, including an object oriented programming language such as Smalltalk, C++ or the like, and conventional procedural programming languages, such as the "C" programming language or similar programming languages.
  • the computer-readable program instructions may execute entirely on the user's computer, partly on the user's computer, as a stand-alone software package, partly on the user's computer and partly on a remote computer or entirely on the remote computer or server.
  • the remote computer may be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or the connection may be made to an external computer (for example, through the Internet using an Internet Service Provider).
  • electronic circuitry including, for example, programmable logic circuitry, field-programmable gate arrays (FPGA), or programmable logic arrays (PLA) may execute the computer-readable program instructions by utilizing state information of the computer-readable program instructions to personalize the electronic circuitry.
  • These computer-readable program instructions may be provided to a processor of a general-purpose computer, special purpose computer, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions/acts specified in the flowchart and/or block diagram block or blocks.
  • These computer-readable program instructions may also be stored in a computer-readable storage medium that can direct a computer, a programmable data processing apparatus, and/or other devices to function in a particular manner, such that the computer-readable storage medium including instructions stored therein comprises an article of manufacture including instructions which implement aspects of the function/act specified in the flowchart and/or block diagram block or blocks.
  • the computer-readable program instructions may also be loaded onto a computer, other programmable data processing apparatus, or other device to cause a series of operational steps to be performed on the computer, other programmable apparatus or other device to produce a computer implemented process, such that the instructions which execute on the computer, other programmable apparatus, or other device implement the functions/acts specified in the flowchart and/or block diagram block or blocks.
  • the schematic flow chart diagrams included herein are generally set forth as logical flow chart diagrams. As such, the depicted order and labeled steps are indicative of one embodiment of the presented method. Other steps and methods may be conceived that are equivalent in function, logic, or effect to one or more steps, or portions thereof, of the illustrated method. Additionally, the format and symbols employed are provided to explain the logical steps of the method and are understood not to limit the scope of the method. Although various arrow types and line types may be employed in the flow chart diagrams, they are understood not to limit the scope of the corresponding method. Indeed, some arrows or other connectors may be used to indicate only the logical flow of the method. For instance, an arrow may indicate a waiting or monitoring period of unspecified duration between enumerated steps of the depicted method. Additionally, the order in which a particular method occurs may or may not strictly adhere to the order of the corresponding steps shown.
  • each block in the flowchart or block diagrams may represent a module, segment, or portion of instructions, which comprises one or more executable instructions for implementing the specified logical function(s).
  • the functions noted in the block may occur out of the order noted in the figures.
  • two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved.
  • modules may be implemented as a hardware circuit comprising custom VLSI circuits or gate arrays, off-the-shelf semiconductors such as logic chips, transistors, or other discrete components.
  • a module may also be implemented in programmable hardware devices such as field programmable gate arrays, programmable array logic, programmable logic devices or the like.
  • Modules may also be implemented in software for execution by various types of processors.
  • An identified module of program instructions may, for instance, comprise one or more physical or logical blocks of computer instructions which may, for instance, be organized as an object, procedure, or function. Nevertheless, the executables of an identified module need not be physically located together, but may comprise disparate instructions stored in different locations which, when joined logically together, comprise the module and achieve the stated purpose for the module.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)
EP19204060.8A 2018-11-27 2019-10-18 Vorrichtung, anordnungen und verfahren zur verringerung des thermischen bogens im rotor eines motors beim anlassen Active EP3660280B1 (de)

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US16/201,601 US11073086B2 (en) 2018-11-27 2018-11-27 Apparatus, assemblies, and methods for mitigating thermal bow in the rotor of an engine at start-up

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CN111219253A (zh) 2020-06-02
US11073086B2 (en) 2021-07-27
EP3660280B1 (de) 2023-01-04
US20200165976A1 (en) 2020-05-28

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